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In order to realize the synchronous control of the roll angle value and the roll angle value of the hypersonic aircraft, so that the aircraft components show a relatively stable motion state, a hypersonic aircraft control system based on differential geometric feedback linearization is designed. Using the power management module circuit, change the connection form of the motor driver components, and debug the real-time operating status of the three subordinate hardware devices of the IMU inertial sensor, GPS positioning, and PID controller according to the rotation rate of the propeller, and complete the main application structure of the hypersonic aircraft control system. design. According to the differential processing result of the aircraft motion trajectory, the specific numerical level of the control vector feedback index is calculated, and then the linearized attitude solution expression is determined by the processing method of the analytical geometric signal, and the aircraft control program design based on the differential geometric feedback linearization is realized. Combined with relevant hardware application equipment, the research on the control system of hypersonic aircraft is completed. The experimental results show that the differential geometric feedback linearization principle can effectively control the roll angle value, the difference level between the pitch roll angle value and the ideal angle value, and has strong feasibility value in promoting the smooth motion of hypersonic aircraft.